# TCDS H11WE: Lassen Air - Type: Type certificate data sheet - Status: Current - Holder: Lassen Air - Revision: 1 - Revised: January 24, 2005 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/d3/c2/d3c24f248871090aeb9eee21e43f022201eed8ffc0c92c8a7b18979fb42e9dab - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5BB0D00D8084438586256F9C0054262B.0001 - Page: https://openairdocs.org/tcds/H11WE ## Models (1) As the data sheet lists them. - CH-21C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H11WE Revision 1 LASSEN AIR Vertol (Army) CH-21C Revised January 24, 2005 TYPE CERTIFICATE DATA SHEET NO. H11WE This data sheet which is a part of ty pe certificate No. H11W E prescribes conditions and limita tions under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: This Type Certificate (TC) has been designated as ABANDONED (See Note 5) Type Certificate Holder Record: Lassen Air P.O. Box 179 Chico, California 95926 I - Model U.S. Army CH-21C (Restricted Category) approved Engine Wright R-1820-103 Fuel 115/145 or 100/130 min. grade Aviation Gasoline Engine limits MP Low Impeller Gear Ratio HP RPM IN HG ALT . Maximum Continuous 1275 2500 46.5 S.L. Maximum Continuous 1275 2500 45.5 2200 Take-Off (5 min) 1425 2700 51.5 S.L. Take-Off (5 min) 1425 2700 50.5 1300 (Straight line manifold pressure variation with altitude). NOTE: Operation at 2600 RPM prohibited. High Impeller Gear Ratio Maximum Continuous 980 2500 43.0 10,800 Maximum Continuous 980 2500 42.0 15,600 Take-Off (5 min) 1100 2600 50.0 9,800 Take-Off (5 min) 1100 2600 49.0 13,000 (Straight line manifold pressure variation with altitude). NOTE: Operation at 2700 RPM prohibited. Rotor Limits and Power Off (Rotor Tach.) Power On (Engine Tach.) Engine Operating Maximum 258 RPM Maximum 2500 RPM Speeds Minimum 233 RPM Minimum 2300 RPM Maximum 2700 RPM; 30 minute limit Airspeed limits Vne (Never exceed) 102 knots IAS Sea Level C.G. range 35 in. fwd. (Sta. 319) to 6.5 in. aft (Sta. 360.5) of datum Datum Point midway between rotors (Sta. 354) Maximum weight 13,500 pounds Minimum Crew 1 (pilot) Fuel capacity Main Fuel Tank 304 Gal. (Sta. 395.0) (300 Gal. usable in forward flight) Page No. 1 2 Rev. No. 1 1 H11WE Page 2 of 2 Revision 1 Oil capacity 21.5 Gal. (Sta. 540.3) Other Operating Department of the Army Technical Manual Limitations TM 55-1520-205-10 "Operator's Manual CH-21Helicopter" dated 1964. Serial Nos. Eligible All Army Serial Nos. Certification basis FAR 21.25(a)(2) effective 1 February 1965, Restricted Type Certificate No. H11WE issued for special purpose of Agriculture Frost Control by air agitation. Date of Application for Type Certificate 18 March 1977. Production basis None. No helicopter may be produced under this type approval. Prior to original Certification of each aircraft, an FAA representative must perform an inspection for workmanship, materials, and conformity with the approved type design. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the helicopter for certification. In addition, equipment necessary for the particular special purpose must be installed. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each helicopter at the time of original airworthiness certification and at all times thereafter. NOTE 2. For placards see Department of the Army, Technical Manual TM 55-1520-205-10. NOTE 3. This model helicopter must be serviced and main tained in compliance with Department of the Army Technical Manual TM 55-1520-205-20, "Organizationa l Maintenance Manual CH-21C helicopter" dated 1964. The retirement times are listed in Chapter 3, Section IV of the Department of the Army Technical Manual TM 55-1520-205-20. NOTE 4. Prior to civil restrictive airworthiness certification, the following must be accomplished: (a) The provisions of AD 60-7-8. (b) The provisions of the following service documents: (1) Piasecki Helicopter Corpora tion SDTM Nos. 1160, 1341, 1377 and 1489. (2) Vertol Aircraft Corporation SDTM Nos. 1568, 1627, 1643, 1662, 1662-1, 1678, 1701, 1714, 1721, 1722, 1727, 1737, 1747, 1750, 1755, 1757, 1773, 1773-1, 1787, 1792A, 1793, 1797, 1798, 1800, 1805, 1815, 1824, 1833, 1834, 1844, 1845 1852, 1859, 1886, 1924, 1952, 1955, 1975, 1980, 1984 and 1986. (3) Boeing Vertol SDTM Nos. 1992, 1999, 1999-1, 2014, 2014-1, 2017, 2025, 2041, 2047, 2047-1, 2052, 2055, 2056, 2056-1 and 2059. (4) Department of the Air Force Technical Order 1H-21-610. (5) Department of the Army Technical Bulle tins TB 55-1520-205-20/7, 34/7 and 34/8 Change No. 1. (6) Department of the Army Modification Work Orders MWO 55-1520-205-20/1 Change No. 1, MWO 55-1520-205-20/2, 34/5, 34/11, 34/17, 34/18, MWO 55-1680-200/20/1 Change No. 2, and MWO 55-2800-201-20/1 change No. 1. NOTE 5. This Type Certificate (TC) has been designated "ABANDONED". A “Notice of Intent To Designate as Abandoned Certain Type Certificates Issued in the Restricted Category,” was published by the Federal Aviation Administration (FAA) in the Federal Register on August 8, 2003 (68 FR 47379). That Notice listed this TC. The FAA received no comments on the published Notice. The FAA has been unable to contact this TC holder. Hence, the FAA has determined that this TC holder is not complying with its Continued Operational Safety (COS) responsibilities. Therefore, no additional aircraft will be added to this TC and no additional original airworthiness certificates will be issued based on this TC. The effectiveness of this TC is limited to those aircraft that received original airworthiness certification prior to the incorporation of this note (Date of Incorporation, January 24, 2005). Subsequently, if the TC holder is located and assumes their COS responsibilities, the restriction(s) imposed by this note may be lifted. .....END..... ``` ## ADs None name its models. ## STCs approved under this data sheet (1) - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.